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    GEARED TURBOFAN WITH THREE TURBINES WITH FIRST TWO COUNTER-ROTATING, AND THIRD CO-ROTATING WITH THE SECOND TURBINE
    31.
    发明申请
    GEARED TURBOFAN WITH THREE TURBINES WITH FIRST TWO COUNTER-ROTATING, AND THIRD CO-ROTATING WITH THE SECOND TURBINE 审中-公开
    带有三台涡轮机的TURBOFAN带第一个两个反转，第三个与第二个涡轮机共旋转

    公开(公告)号：WO2014007893A3

    公开(公告)日：2014-02-27

    申请号：PCT/US2013034324

    申请日：2013-03-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

    IPC: F01D5/02 ,  F02C7/00

    CPC classification number: F16J15/0887 ,  F01D15/12 ,  F02C3/067 ,  F02C7/36 ,  F02K3/072 ,  Y02T50/672

    Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool, with the high speed spool rotating in an opposed direction to the intermediate speed spool. The fan drive turbine rotates in the same direction as the intermediate speed spool.

    Abstract translation: 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子。 第二压缩机转子将空气压缩至比第一压缩机转子更高的压力。 第一涡轮转子驱动第二压缩机转子和第二涡轮转子。 第二个涡轮驱动压缩机转子。 风扇驱动涡轮机定位在第二涡轮机转子的下游。 风扇驱动涡轮通过齿轮减速来驱动风扇。 第一压缩机转子和第二涡轮机转子作为中速卷轴旋转。 第二压缩机转子和第一涡轮转子一起作为高速卷轴，高速卷轴沿与中速卷轴相反的方向旋转。 风扇驱动涡轮以与中速阀芯相同的方向旋转。

    VARIABLE AREA TURBINE
    32.
    发明申请
    VARIABLE AREA TURBINE 审中-公开
    可变面积涡轮机

    公开(公告)号：WO2013165512A3

    公开(公告)日：2013-12-19

    申请号：PCT/US2013025727

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

    IPC: F01D17/16 ,  F02C7/042

    CPC classification number: F01D17/162 ,  F02C9/22 ,  F05D2270/112 ,  F05D2270/3032

    Abstract: A gas turbine engine includes a shaft and a turbine configured to drive the shaft. The turbine has at least one stage comprising a plurality of turbine vanes interspersed with a plurality of turbine blades. The plurality of vanes includes at least one variable vane movable between a closed position to reduce air flow and an open position to increase air flow. Movement of the at least one variable vane is controlled based on an engine limiting condition.

    Abstract translation: 燃气涡轮发动机包括轴和配置成驱动轴的涡轮。 涡轮机具有至少一个级，其包括散布有多个涡轮叶片的多个涡轮叶片。 所述多个叶片包括至少一个可变叶片，所述至少一个可变叶片可在关闭位置和减小气流的打开位置之间移动，以增加气流。 基于发动机限制条件来控制至少一个可变叶片的运动。

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    35.
    发明专利
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 未知

    公开(公告)号：SG10201901074VA

    公开(公告)日：2019-03-28

    申请号：SG10201901074V

    申请日：2013-01-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

    Abstract: GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE OF THE DISCLOSURE A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine. Fig. 2

    GAS TURBINE ENGINE WITH MOUNT FOR LOW PRESSURE TURBINE SECTION
    37.
    发明专利
    GAS TURBINE ENGINE WITH MOUNT FOR LOW PRESSURE TURBINE SECTION 未知

    公开(公告)号：CA2945264A1

    公开(公告)日：2017-05-05

    申请号：CA2945264

    申请日：2016-10-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  GLAHN JORN A

    IPC: F02C7/00 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F02C9/00

    Abstract: A turbine section of a gas turbine engine according to an example of the present disclosure includes, among other things, a first turbine section and a second turbine section. The first turbine section has a first exit area and rotates at a first speed. The second turbine section has a second exit area and rotates at a second speed. A first performance quantity is defined as the product of the first speed squared and the first exit area. A second performance quantity is defined as the product of the second speed squared and the second exit area.

    GEARED TURBOFAN ENGINE WITH POWER DENSITY RANGE
    40.
    发明专利
    GEARED TURBOFAN ENGINE WITH POWER DENSITY RANGE 未知

    公开(公告)号：CA2916866A1

    公开(公告)日：2016-07-09

    申请号：CA2916866

    申请日：2016-01-06

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

    IPC: F02K3/06 ,  F02C3/04 ,  F02C7/36

    Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in a second direction opposed to the first direction.

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